System for cooling turbopumps used in cryogenic fluid storage facilities is described. Technique uses thermodynamic propellant vent to intercept pump heat at desired conditions. Cooling system uses hydrogen from outside source or residual hydrogen from cryogenic storage tank

Mckee, H. B.

Patten, T. C.

English

NASA Technical Reports Server

July 1972	 B72-10408 
NASA TECH BRIEF 
Marshall Space Flight Center 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage 
commercial application. Tech Briefs are available on a subscription basis from the National Technical Information 
Service, Springfield, Virginia 22151. Requests for individual copies or questions relating to the Tech Brief program may 
be directed to the Technology Utilization Office, NASA, Code KT, Washington, D.C. 20546. 
Turbopump Thermodynamic Cooling 
Pump Enclosure	 2.54 cm (1 Inch) 
2.54 cm (1 Inch)	 Micro Quartz	 Structural Support ation (Heat Short—For Insul	
/ Rapid Cool—Down) 
Shaft jR{
	
Turbine C	
._- Heat Source 
W\
31.6 kJ/hr  4	 _________ (30 BTU/hr)	 _______	 RII4) 
137 kJ/hr	 74 kJ/hr	 l
32 kj/hr 
20 BTU/hr) 
TU/hr)(7BIU/hL232 kJ/hr 
Line
a 
A large amount of the heat in cryogenic systems 
comes from operation of the turbopumps. The hot 
turbine gas delivers this heat by conduction down the 
shaft into the propellant. Additional heating also comes 
from radiation from the pump enclosure and from 
conduction from the feed lines. This heat flux must be 
eliminated to avoid excessive propellant heating which 
could result in pump cavitation. Previous cryogenic 
turbopump systems required a chill-down period for the 
pumps prior to start-up. 
The developed technique uses a thermodynamic 
propellant vent to intercept the pump heat at the 
desired conditions. It is applicable to multiple-start 
turbopump systems that use liquid hydrogen or to any 
system located near a liquid hydrogen supply that 
requires continuous cooling. The technique uses either
Use of the thermodynamic propellant vent to main-
tain pump temperature greatly reduces the amount of 
propellant required to accommodate the heat load and 
allows pump start-up at any time. This configuration is 
well suited to systems which operate on demand where 
pump start-up cannot be accurately predicted. During 
operation of the thermodynamic vent system, liquid 
hydrogen is withdrawn from a propellant storage tank 
and expanded through a throttle device. After expansion, 
the liquid hydrogen, partially vaporized, is at low 
pressure at a temperature 4°K (7 0R) below the initial 
liquid temperature. This two-phase mixture then absorbs 
the required heat until it is completely vaporized. 
In the thermodynamic pump model, shown in -the 
figure, the coolant is routed down the shaft and vented 
overboard. This allows the coolant to be heated above 
the propellant temperature as it flows down the shaft 
and minimizes the coolant flow required. Housing 4W. hydrogen provided for the purpose or liquid hydrogen residuals which are not otherwise utilized.
(continued overleaf) 
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https://ntrs.nasa.gov/search.jsp?R=19720000407 2020-03-17T03:39:04+00:00Z
coolant-flow is utilized to maintain the housing temper-
ature at or near the propellant temperature. Because the 
hydrogen housing coolant would still have a significant 
amount of heat capacity available above 22°K (400R), 
it is routed to the oxygen turbopump. Sufficient heat 
capacity is available to meet the oxygen cooling re-
quirements. The unique features of the innovation 
minimize the pump chill-down and boil-off losses, 
maintain turbopumps in a chilled state for a start at all 
times, and cut coolant requirements by almost fifty 
percent.
Notes: 
1. Information concerning this innovation may be of 
interest to cryogenic pump manufacturers. 
2. Requests for further information may be directed to: 
Technology Utilization Officer 
Marshall Space Flight Center 
Code A&TS-TU 
Huntsville, Alabama 35812 
Reference: B72-10408 
Patent status: 
No patent action is contemplated by NASA. 
Source: T. C. Patten, H. B. McKee of 
McDonnell-Douglas Corp. 
under contract to
Marshall Space Flight Center 
(MFS-2 1 597) 
B72-10408	 Category 06


Turbopump thermodynamic cooling

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